Abstract: An apparatus for controlling the temperature of a component, which is situated in use in a gas stream, provides a nozzle to create a jet of air at an angle to the gas stream, the jet being directed into the region of the stagnation point of the component so as to control the temperature of the component. The invention is particularly suited to preventing or reducing the formation of ice on vanes of gas turbine engines, but may also be applied to other components, and may equally be used in situations where a component is to be cooled rather than heated.

Abstract: A lubrication scavenge system is disclosed herein. The lubrication scavenge system includes a sump housing substantially encircling a structure disposed for rotation about an axis. The sump housing has an inwardly-facing surface extending at least partially about the axis in a spiral path. The spiral path increases in radial distance from the axis in the direction of rotation of the structure, in a plane perpendicular to the axis. The spiral path extends 360°.

Abstract: A steam turbine has a two-shell housing, including an outer casing and an inner casing arranged therein, as well as a pipe that extends through the outer casing for supplying and/or removing steam to or from the inner casing, the pipe being provided with a pair of apertures arranged opposite each other on the inner casing. According to the invention, a first steam supply or discharge pipe can be connected to a first aperture, and the second aperture is closed by a cover.

Abstract: A centrifugal turbocompressor including an open-type impeller and a casing compresses a gaseous body that condenses into a liquid. The compressor suppresses erosion due to accumulation of a liquid on a casing surface in the compressor. Such accumulation is possible during the starting time of the compressor, if the gaseous body that has come into contact with the casing condenses on the surface of the casing and changes into liquid droplets, centrifugal force may cause the droplets to accumulate on the surface of the casing positioned outside an impeller, and thus to grow into coarser and larger droplets or a liquid film. If the blade tips of the impeller rotating at high speed scrape the droplets or the film upward, erosion of the blade tips is liable to result.

Abstract: A gas turbine engine is provided comprising a compressor with an insulated cooling circuit. The compressor comprises a compressor casing having a compression chamber and at least one stator and at least one rotor disposed in the compression chamber, the at least one stator comprising a stator body having a plurality of tubes for transporting cooling air through passages in the stator body into the compression chamber. The plurality of tubes are surrounded by an air gap for insulating the tubes from the stator body.

Abstract: An inter-turbine casing for a turbofan is disclosed. The casing includes an outer ring, an inner ring, and an intermediate ring between the inner ring and the outer ring. The inner and intermediate rings have respective openings for the passage of cooling air. The casing includes at least one sealing device, arranged between the outer ring and the intermediate ring, with a base, provided with at least one orifice for the passage of cooling air, and a peripheral skirt which is able to be compressed and expanded elastically. The base bears against the outer ring and the peripheral skirt bears against the intermediate ring.

Abstract: In one embodiment, a turbine system may include a turbine casing, a shroud block coupled to the turbine casing, a fluid passage in the shroud block; and a pin configured to interface with the fluid passage. The pin may include a hollow shaft; a rod inserted into the hollow shaft; and a valve disposed on a distal end of the rod, wherein the valve is configured to open and close the fluid passage when the rod is actuated remotely through the hollow shaft.

Abstract: A turbine cooling component comprising a circumferential leading edge, a circumferential trailing edge, a pair of spaced and opposed side panels connected to the leading and trailing edges, an arcuate base connected to the trailing and leading edges having a fore portion, a midsection portion, an aft portion, opposed side portions, an outer surface partially defining a cavity operative to receive pressurized air, and an arcuate inner surface in contact with a gas flow path of a turbine engine, a first side cooling air passage in the base extending along the first side portion from the fore portion to the aft portion, and a fore cooling air passage in the fore portion of the base communicative with the side cooling air passage and the cavity, operative to receive the pressurized air from the cavity.

Abstract: A mount includes a mounting bolt attached to a casing; an internal bushing that engages the casing at a distal end of the internal bushing; and an external bushing that engages a manifold and engages the internal bushing. The internal bushing is adjustable with respect to the external bushing thereby allowing the manifold to be adjustable with respect to the casing.

Abstract: A centrifugal blower (10) includes a casing (12) and a rotor (14) rotatable disposed in the casing. The casing includes a base plate (121), a sidewall (122) extending from the base plate and a cover (123) covering the sidewall. The sidewall is a multilayer structure and includes a first section (128a) and a second section (128c). A distance between a central axis (A) of the rotor and an inner surface of the second section is greater than that between the central axis of the rotor and an inner surface of the first section. The first section is located below a mother board (20) and the second section sits on a top surface of the motherboard when the centrifugal blower is mounted to the mother board.

Abstract: According to one embodiment, an electronic apparatus is provided with a housing, a circuit board in the housing, fan blades configured to rotate and blow air in a centrifugal direction, and a casing which contains the fan blades. The casing includes an exhaust port and a cut portion which opens in a centrifugal direction different from a direction in which the exhaust port opens, from a perspective of a rotation center of the fan blades, and into which a part of the circuit board is inserted.

Abstract: An embodiment of the present invention may provide an integrated cooling system for multiple compartments of a turbomachine. The cooling system, in accordance with embodiments of the present invention, may provide the following benefits to the user. Improvement on the combined cycle efficiency and an increase in the power output. This may result from reducing the exhaust dilution losses and reducing the parasitic load by requiring fewer air circulation devices. The present invention may also benefit the user by reducing the installation and start-up costs of the cooling system by requiring fewer air circulation devices and integrating the cooling systems. The present invention may circulate a cooling fluid through an integrated cooling circuit, which may be in fluid communication with each compartment of the multiple compartment of the turbomachine.

Abstract: A seal gas recovery method including introducing a first seal gas stream to a first mechanically coupled booster/expander assembly, where the first booster/expander assembly includes a first booster, a first expander, a first shaft that mechanically couples the first booster and the first expander, and a first seal on the first shaft. The method further includes removing at least a portion of a first recoverable gas stream from the first seal, where the first recoverable gas stream includes at least a portion of a first process leak gas stream and at least a portion of a first seal gas vent stream. The method further includes introducing a second seal gas stream to a second expander assembly, where the expander assembly includes a second expander, a second shaft, and a second seal on the second shaft.

Abstract: Cooling air manifold splash plates and gas turbine engine systems involving such splash plates are provided. In this regard, a representative cooling air manifold splash plates includes: a base having an aperture; and an air deflector supported by the base, the air deflector being positioned relative to the base to receive, from the aperture, a radial flow of gas turbine engine cooling air, the air deflector being operative to redirect at least some of the air received circumferentially.

Abstract: An active tip clearance control (ATCC) apparatus of an aircraft gas turbine engine is situated within a pressurized core case of the engine. First and second portions of bypass air flow passing through the respective compressed core compartment and the ATCC apparatus, are isolated from one another in order to improve both the ATCC performance and bypass air duct performance.

Abstract: A gas turbine engine has a plurality of radial struts in a bypass duct. At least one strut has a scoop incorporated with the fairing of the strut and in communication with an air passage of an engine secondary air system. The scoop faces a bypass air flow to scoop a portion of the bypass air flow using available dynamic pressure in the bypass duct. Scooped air may be provided, for example, to an active tip clearance control apparatus in a long duct turbofan engine.

Abstract: A shroud suitable for use in a gas turbine engine exhibits substantially uniform thermal growth.

Abstract: An internal heating arrangement for a centrifugal impeller for a gas turbine engine is provided having at least one heating passage extending through into the rotor for directing air bled from the rotor exit along the backface and forwardly through the impeller.

Abstract: An active heat-dissipating mechanism includes a fan module, an airflow-guiding part and an airflow shunt part. The fan module includes an airflow inlet and an airflow outlet. The airflow-guiding part is disposed at the same side of the airflow outlet of the fan module and in communication with the fan module. An airflow channel is defined by the airflow-guiding part. An airflow inhaled by the fan module is guided to a hotspot region of the electronic device through the airflow channel so as to remove the heat generated from the hotspot region. The airflow shunt part is formed on the airflow-guiding part. The airflow shunt part defines a stopping block in the airflow channel. A portion of the airflow is hindered by the stopping block and guided into a sub-hotspot region of the electronic device so as to remove the heat generated from the sub-hotspot region.

Abstract: A heating and cooling system for a wind turbine is provided and includes a gearbox, gearbox heat exchanger, generator, generator heat exchanger, and a cooling duct. The cooling duct is connected to the gearbox and generator heat exchangers, and is used to transport air across both heat exchangers to cool the gearbox and generator.

Abstract: A method is disclosed for improving a turbine's thermal response during transient and steady state operating conditions in which the flow of cooling fluid in the turbine's casing is caused to be asymmetrical relative to the horizontal and vertical symmetry planes of the casing so that the turbine's cooling symmetry planes are rotated relative to its geometric symmetry planes and thereby the heat transfer at locations in the casing with increased mass is increased.

Abstract: Apparatus for channeling combustion gases to a turbine in a gas turbine engine. The engine has a compressor for providing compressed air, a combustor for combusting fuel with the compressed air to provide combustion gases, and a radial inflow turbine having an inlet configured to receive the combustion gases. The turbine is rotatable about an axis for expanding the combustion gases to produce work. The apparatus includes a subassembly of plurality of nozzle guide vanes fixed between a pair of spaced apart, ring-shaped sidewalls. A pair of spaced apart supports is configured to position the subassembly therebetween, concentric with the axis, and adjacent the turbine inlet. The apparatus further includes a plurality of bolt assemblies extending axially through the pair of supports, apertures in the sidewalls, and holes in the guide vanes.

Abstract: An exhaust eductor system includes a primary exhaust nozzle configured to transport an active flow stream; and a mixing duct at least partially surrounding the primary exhaust nozzle and configured to transport a passive flow stream that is entrained by mixing with the active flow stream from the primary exhaust nozzle. The mixing duct has an interior, and a baffle on the interior of the mixing duct is configured to prevent the mixed flow streams from exiting the mixing duct.

Abstract: A blade tip shroud segment for a gas turbine engine in which the shroud segment is cooled and sealed using a combination of vortex cooling air flow and cooling air discharge film cooling. The shroud segment includes a row of vortex chambers formed within the shroud segment and a row of circumferential circular grooves formed on the hot gas flow surface of the shroud segment, where each groove is connected to a vortex chamber through a slot. Cooling air is to the vortex chambers from individual cooling air feed slots or through inter-linking channels connecting adjacent vortex chambers.

Abstract: A steam turbine comprises a rotor with moving blades attached thereto; diaphragms which surround the rotor from an outer periphery side of the rotor; a casing which encloses the diaphragms and the rotor and has an upper half and a lower half clamped together through respective flanges; a displacement detector for measuring a difference d in thermal expansion in the rotor axis direction between the casing and the rotor; heating/cooling devices attached to the flanges respectively to heat and cool the flanges; and a controller which makes control so that the flanges are heated or cooled by the heating/cooling devices until a measured value obtained by the displacement detector reaches a preset value M or S in unsteady operation.

Abstract: Gas turbine engine systems and related methods involving heat exchange are provided. In this regard, a representative heat exchange system for a gas turbine engine includes: a heat exchanger; and a flow restrictor operative to selectively restrict a flow of gas flowing along an annular gas flow path; in an open position, the flow restrictor enabling gas to flow along the gas flow path and, in a closed position, the flow restrictor restricting the flow of gas such that at least a portion of the gas is provided to the heat exchanger, the heat exchanger being located radially outboard of the flow restrictor.

Abstract: A system for ventilating a downstream cavity of an impellor of a centrifugal compressor in a turbomachine, this system including flow diversion system mounted fixedly in the downstream cavity of the impellor in order to divert the ventilation air taken from the outlet of the compressor and cause it to circulate radially from the inside to the outside along the downstream face of the impellor.

Abstract: A impingement cooling system for heavy duty turbines that includes a manifold affixed to a casing of the heavy-duty turbine, wherein the manifold includes a plurality of impingement holes in the surface of the manifold and a blower that provides air flow across the plurality of impingement holes of the manifold to cool the casing of the heavy-duty turbine to control the clearance between a tip of a turbine blade and a shroud of the heavy-duty turbine.

Abstract: A centrifugal fan includes a cylindrical housing for housing an impeller, a motor for driving the impeller and a disk-like circuit board that are arranged coaxially in an accumulated manner. When the impeller rotates, air is taken in along the axial direction of the housing and goes out through an air outlet disposed in the circumference surface of the housing. A ring-like air inlet is disposed in a wall face on one side of the housing in the axial direction. An outer rim of the circuit board that is disposed inside the wall face is substantially within the inside edge of the air inlet, and a self-heating electronic component is mounted on the circuit board at the outer edge portion. A part of air taken in from the air inlet flows at a vicinity of the electronic component so that the electronic component is cooled.

Abstract: A method and apparatus for scavenging lubricant is disclosed herein. In the invention, a rotating structure is encircled within a sump housing and subjected to lubrication. The sump housing collects high-momentum lubricant flow and low-momentum lubricant flow. The interior of the sump housing is separated into a plurality of chambers with at least one dynamic seal. The at least one dynamic seal extends between the sump housing and the rotating structure to isolate the high-momentum lubricant flow from the low-momentum lubricant flow.

Abstract: A turbine engine that includes a vortex protrusion disposed upon a component that rotates during operation of the turbine engine; wherein the vortex protrusion includes an outer surface that is configured to induce a vortex flow pattern as the component rotates during operation.

Abstract: The object of this invention is, in an electronic device provided with a supporting member that supports a drive member driven with vibration by engaging therewith, to provide the fixing structure of wiring that realizes the following: alleviation of the wobble generated by the vibration at the operating time of the drive member, reduction of unwanted sound and vibration caused by the above wobble, and inexpensive fixing of a wire without additional and specific members for wiring. This invention is constituted as a fixing structure of wiring for fixing a wire wired in an electronic device, wherein a drive member driven with vibration and a supporting member for supporting the drive member by engaging therewith are provided in the electronic device, and wherein the wire is fixed by being interposed in a gap formed between the drive member and the supporting member.

Abstract: A gas turbine engine plasma blade tip clearance control system includes an annular shroud surrounding rotatable blade tips and an annular plasma generator spaced radially outwardly and apart from the blade tips. An exemplary embodiment of the annular plasma generator is mounted to the annular shroud and includes radially inner and outer electrodes separated by a dielectric material disposed within an annular groove in a radially inwardly facing surface of the annular shroud. The plasma generator is operable for producing an annular plasma between the annular shroud and blade tips and an effective clearance produced by the annular plasma between the annular shroud and blade tips that is smaller than a clearance between the annular shroud and blade tips.

Abstract: A showerhead film cooling hole arrangement for a turbine blade used in a gas turbine engine. The showerhead includes at least three rows of film cooling holes with the middle row arranged along the stagnation point. A second row of film cooling holes is arranged on the pressure side of the first row, and a third row of film cooling holes is arranged on the suction side of the first row. Each of the three rows includes a diffusion opening in which the diffusion is expanding in the outward direction or the inward direction with an angle from greater than zero degrees to around 5 degrees.

Abstract: A fan attachment is provided to attach a fan assembly to a cap of a heat exchanger. The fan attachment includes a feature to manage wires going to the fan motor, a notch for a thermister to sense temperature, snap hooks to be engaged by receiving tabs of the cap, a keying shear load feature to radially align the fan attachment and cap, and Z-height tolerance springs to bias the fan attachment away from the cap. The cap has features to interact with those of the fan attachment, including receiving tabs. The fan attachment may be manually aligned and forced so that the snap hooks are received and engaged by the receiving tabs. Additionally, the snap hooks and keying feature are, in combination, capable of supporting fan and attach mechanism in an undamaged condition during 25 g-force shock to the heat exchanger.

Abstract: A fan housing with a noise-reducing structure includes a housing having a side wall. An air inlet is defined in the housing and an air outlet defined in the side wall of the housing. A plurality of supporting ribs are disposed in the air inlet and connected between inner and outer peripheries of the air inlet for supporting a motor base. At least one of the supporting ribs is adjacent to the air outlet and extends in a direction coincident to or intersects with a longitudinal line of the air outlet extending through a rotational axis of the motor base.

Abstract: A heat dissipation device (1) includes an electric fan (20) and a heat sink (10). The fan includes a fan impeller (40) which includes a hub (41) and a plurality of blades (42) extending radially and outwardly from the hub (41). The hub (41) includes an upper portion (417) and a bottom portion (413). An air inlet (411) is formed near the upper portion (417) and an air outlet (412) is formed near the bottom portion (413). The blades (42) have portions on the bottom portion of the hub which are extended toward a center of the air outlet for driving more air to the center of the air outlet (412), whereby more air can flow to a center of the heat sink.

Abstract: A cooling system of a gas turbine engine, includes a heat exchanger having a common wall shared by a first air passage for directing a portion of a compressor air flow to be used as cooling air, and a second air passage for directing a portion of a bypass air flow, the portion of the compressor air flow being thereby cooled by the portion of the bypass air flow through the common wall

Abstract: A system and method for actively managing blade tip clearances in a turbine engine, particularly under steady state operating conditions such as at base load, involves routing a portion of air from a rotor cooling air circuit to a vane carrier or other stationary support structure surrounding the turbine blades. Because the temperature of the air is less than the temperature of the stationary support structure, the stationary support structure will thermally contract when the air is passed in heat exchanging relation therewith. In one embodiment, the air can be passed through one or more passages extending through at least a portion of the stationary support structure. The contraction of the stationary support structure reduces the blade tip clearance because the blades do not contract. Thus, fluid leakage through the clearances is minimized, which in turn can increase engine performance.

Abstract: A heat dissipation module for an electronic device includes a base disk, a suction disk, a water guide and a cover. The base has a containing space and a plurality of cooling strips. The suction base is attached to the base disk and further includes a water chamber for receiving sucked water, an inlet and an outlet. The water guide is attached to the suction disk with a guide port at the periphery thereof. The cover closes the suction disk and is movably joined to a guide fan. When the heat dissipation module is full with fluid, the fluid can flow therein rapidly while the guide fan rotating such that the fluid is discharged from and flows into the heat dissipation module more effectively.

Abstract: The invention relates to a device for cooling a housing of a gas turbine and/or of a combustion chamber, in particular of a gas turbine, comprising: a cooling gas supply device with a cooling gas outlet, out of which a cooling gas stream flows when the cooling gas supply device is in operation, and with a cooling gas inlet, via which the cooling gas stream flows back to the cooling gas supply device when the cooling gas supply device is in operation; and a cooling gas path which is led through the housing in the circumferential direction of the latter and which connects a first housing connection to a second housing connection. So that a circumferential temperature difference of the housing can be set independently of an average temperature of the housing, the cooling device is equipped with a switching device for reversing the flow direction.

Abstract: A drain pump is provided that reduces the operating noise when the head is low. The drain pump has a pump casing, and an impeller. The pump casing has a drain inlet for sucking in drain water at a lower end part and a drain outlet for discharging drain water at a side part. The impeller has a shaft part disposed extending in a vertical direction inside the pump casing, a main blade disposed on the outer circumferential side of the shaft part, an auxiliary blade disposed on the lower side of the main blade, and a disc shaped dish part disposed between the main blade and the auxiliary blade. The dish part has an annular partition part extending upward from the outer circumferential edge part of the main blade, which is disposed at a position lower than the upper end part of the partition part.

Abstract: A system for ventilating a downstream cavity of an impellor of a centrifugal compressor in a turbomachine, this system comprising flow diversion means (70, 84) mounted fixedly in the downstream cavity (38) of the impellor (36) in order to divert the ventilation air taken from the outlet of the compressor (10) and cause it to circulate radially from the inside to the outside along the downstream face (34) of the impellor.

Abstract: Electronic equipment frequently requires cooling to maintain the integrity and reliability of the equipment, and to elongate the life expectancy of the equipment. When in operation, the fan of a UAV creates airflow comprising outside air directed across the duct of the UAV. Utilizing this airflow generated by the fan of a UAV to provide heat transfer from a equipment enclosure accomplishes efficient heat transfer. The methods described herein for transferring heat from an equipment enclosure using an airflow generated by a fan of a UAV may be employed for UAVs having a variety of duct shapes, and having equipment enclosures inside the duct or in detachable equipment enclosures located on the duct of the UAV.

Abstract: A super steam turbine (100) into which high-temperature steam of 650° C. or more is introduced is provided with an inner steam pipe (120) which is disposed through an inner casing (110) and an outer casing (111), an outer steam pipe (130) which is welded to the outer casing (111) and disposed outside of the inner steam pipe (120) along the inner steam pipe (120) with a prescribed space therebetween, and a radiation heat shielding pipe (140) which is disposed along the inner steam pipe (120) between the inner steam pipe (120) and the outer steam pipe (130) to face a welded portion of at least the outer steam pipe (130), wherein cooling steam (160) is flown between the inner steam pipe (120) and the outer steam pipe (130), respective component parts are made of a suitable heat-resisting steel having prescribed chemical composition ranges.

Abstract: A method for cooling a component of a turbine is provided, wherein a fluid with a pressure below 1 bar is guided away from the component. Moreover, a turbine is described comprising a component, a conduit which is connected to the component so that a fluid can be guided away from the component, and a fluid discharge which is connected to the conduit. The fluid discharge is constructed so that it removes a fluid with a pressure below 1 bar.

Abstract: A blade outer air seal is provided with a plurality of distinct cooling circuit schemes. Preferably, compact heat exchanger structures are utilized, and can be individually tailored to the particular location along the blade outer air seal. As an example, a greater pressure ratio exists between the products of combustion and the cooling air at the trailing edge than would be found at the leading edge. The present invention takes advantage of this distinction by utilizing cooling schemes that have a greater pressure drop at the trailing edge than the cooling schemes utilized closer to the leading edge.

Abstract: A blade outer air seal used in a gas turbine engine, the BOAS including a metering plate with metering holes and an impingement plate with impingement holes, the metering plate and impingement plate forming a plurality of separate diffusion cavities forming a grid. A porous metallic plate is bonded to the underside of the impingement plate and has a plurality of cooling channels extending from the leading edge to the trailing edge of the BOAS. Cooling air from the blade ring carrier is metered through the metering holes and into the diffusion cavities, and then passes through a plurality of impingement holes and into a cooling channel, to be discharged out the trailing edge side of the BOAS. Inter-segment cooling holes also pass cooling air out to the sides of the BOAS.

Abstract: The invention relates to a rotor for a non-positive-displacement machine provided with a hollow shaft, which is arranged coaxial to the rotation axis, is supported, on both sides and on the face, on two axially opposed sections of the rotor, and which encloses an inner hollow space. In order to provide a rotor for a non-positive-displacement machine, which has a higher serviceable life and is less susceptible to mechanical defects, the invention provides that the hollow shaft, in the axial direction of the rotor, is formed from a number of adjoining rings, and the rings are outwardly sealed against one another an with regard to the sections of the hollow space. Each ring has an I-shaped cross-section and the web of the I shape extends in the radial direction of the rotor.

Abstract: A fan with supercharging device has a hub and fan blades. A hub has a shape similar to a cone with a tip end and a circumferential side. The fan blades extend radially from the circumferential side of the hub. Each of the fan blades has a joining end being attached to the circumferential side, a free end extending outward the hub and a front edge and a rear edge being between the joining end and the free end respectively. The rear edge of the respective fan blade is shielded by the front edge of another fan blade next to it. The unshielded portion of the respective fan blade has an area gradually increases from the joining end to the free end. A projection is disposed at the free end along a direction of fluid flow. Hence, fluid pressure is capable of increasing significantly while the fan is in operation.